Structural Tailoring of Advanced Turboprops (STAT) · 2013-08-30 · This manual describes the programming aspects of the Structural Tailoring of Advanced Turboprops (STAT) system

NASA Contractor Report 182164

Structural Tailoring of Advanced Turboprops (STAT)

Programmer's Manual

K. Brown UNITED TECHNOLOGIES CORPORATION Pratt & Whitney 400 Main Street East Hartford, CT 06108

Prepared for Lewis Research Center Under Contract NAS3-23941

National Aeronautics and Space Ad ministration

https://ntrs.nasa.gov/search.jsp?R=19890010761 2020-03-29T07:55:39+00:00Z

PREFACE

This manual describes the programming aspects of the Structural Tailoring of Advanced Turboprops (STAT) system. The manual is divided into seven main sections, each of which describe module intent and interaction within the STAT program. Section 1 discusses the overall program flow and categorization of the modules. The ADSREAD subsystem, which provides a means for the analysis modules to access a description of the current blade design, is described in Section 2. The function of each high-level module is given in Section 3. The file units and common blocks are described in Sections 4 and 5, respectively. Section 6 describes the method in which refined analysis modules can be added to the program, and Section 7 defines the job control language for the CRAY COS version of STAT.

i

STRUCTURAL TAILORING OF ADVANCED TURBOPROPS (STAT) PROGRAMMER ' S MANUAL

Table o f Contents

Page

1

Sect ion

1.0 INTRODUCTION

1.1 Program Descr ip t ion 1.2 Categor iza t ion o f Modules

3 3

2.0 THE ADSREAD SUBSYSTEM 4

3.0 PROGRAM FLOW CHARTS 5

3.1 3.2 3.3 3.4 3.5 3.6 3.7 3.8 3.9 3.10 3.11 3.12 3.13 3.14 3.15 3.16

Main Program STAT I N ASSOCS OPT003 OPT009 ADS EFFICH BDS FEARUN FLUTER GAEROH DBNF ONEPFR OBJF DEFCON REPORT

5 7

9 10 12 14 15 16 17 19 20 21 22 23 24

a

4.0 FILE U N I T S 25

5.0 STAT COMMON BLOCKS 26

5.1 Common Blocks Sorted b y Rout ine 33

6.0 ADDING REFINED ANALYSIS MODULES TO STAT 42

6.1 Work Storage Array 44

7.0 JCL FOR THE CRAY COS VERSION OF THE STAT PROGRAM 45

7.1 Execut ing t h e STAT Program 45

8.0 REFERENCES 46

DISTRIBUTION LIST 47

ii

1.0 INTRODUCTION

The Structural Tai 1 ori ng of Advanced Turboprops (STAT) computer program was developed t o perform numerical optimizations on h ighly swept propfan blades. The optimization procedure seeks t o minimize an objective function, defined as e i ther d i rec t operating cost o r aeroelastic differences between a blade and i t s scaled model, by t u n i n g internal and external geometry variables tha t must sa t i s fy real i s t i c blade design constraints.

The STAT analyses include an aerodynamic efficiency evaluation, a f i n i t e element s t r e s s and v i bration analysis, an acoustic analysi s, a f l u t t e r analysis, and a once-per-revol u t i o n (one-p) forced response 1 i f e prediction capabil i t y . The STAT constraints incl ude b l ade s t resses , bl ade resonances, f l u t t e r , t i p displacements and a one-p forced response l i f e fraction. The STAT vari ab1 es i ncl ude a1 1 b l ade internal and external geometry parameters needed t o define a composite material blade. The STAT objective function i s dependent upon a blade baseline definit ion which the user supplies t o describe a current blade design for cost optimization or for the ta i lor ing of an aeroelastic scale model.

To perform a blade optimization, three component analysis categories are required: an optimization a1 gori t h m ; approximate analysis procedures for objective function and constraint evaluation; and refined analysis procedures for optimum design validation. The STAT computer program contains an executive control modul e , an o p t i m i zer, and a1 1 necessary approximate and refined analyses. The optimization algorithm of STAT i s the Automated Design Synthesis (ADS) optimization package, which i s a proven tool for optimizations w i t h a small t o medium (1 t o 30) number of design variables. A flowchart of the STAT procedure i s shown i n Figure 1 .

The approximate analyses of STAT u t i l i z e an e f f i c i en t , coarse mesh, plate f i n i t e el ement bl ade v i bration analysi s procedure. The f i n i t e el ement analysi s provides blade natural frequencies and mode shapes, s t r e s s under centrifugal and pressure 1 oads, and bl ade weight. Additional constraint eval uati ons, i n c l u d i n g f l u t t e r , power, acoustic and one-p ca l cu la t ions , u t i 1 ize o u t p u t from the f i n i t e el ement analysis.

After each completed design i t e r a t ion , the current design i s verified by applying refined analyses t o assure tha t a l l constraints a re sa t i s f ied . If the constraints a re not a l l s a t i s f i ed , then correction factors are applied t o the approximate analyses t o bet ter cal i brate them w i t h the refined analyses resul ts . The optimization process continues t o the next completed design move u n t i l a local optimum design has been found whose constraints sa t i s fy refined analyses.

To use the blade optimization system, design variable (parametric) curves used t o describe the external and internal geometry o f a turboprop fan blade must be defined. External geometry curves define b lade thickness, section stacking, camber, chord, twist and conical sections. Internal geometry curves define individual 1 ayer thickness, percent chord coverage and position over the ent i re b l ade.

( INPUT]

[ I N I T I ~ Z L ~

STAT PROCEDURAL OUTLINE

1-4 BEGIN OPTIMIZATION LOOP

PRINT COMPARISON TABLE OF REFINED VS. APPROXIMATE

---------- > Read user input file defining blade

.------ > Initialize design curves, ADS, and cakxlate initial ai-.

and optimization parameters.

--- > Successive calls to ADS, FEA, Flutter, Aero, Acoustic, 1 -P Forced Response, Objed i and Constraintcalcuhtions.

-I-- > Successive calls to refined FEA, FMter. Aero and Acoustic calculations.

T

STOP]

Figure 1 Structural Tail o r i ng of Advanced Turboprops Overall Program F1 ow

The STAT system has been applied t o the Large-Scale Advanced Propfan ( L A P ) SR-7 blade, the LAP SR-7 aeroelastic scale model blade and the 18E SR-7 infeasible blade des ign , as detailed i n Reference 1 . The STAT program made s ignif icant improvements i n a l l three cases and demonstrated the great potential fo r design enhancements through the application of numerical optimization t o turboprop fan blades of composite construction.

This manual describes the functionali ty of the STAT system from a programmer's viewpoint. I t provides a top-down description of module intent and interaction. The purpose of this manual i s t o familiarize the programmer w i t h the STAT system so t h a t he/she may enhance o r verify the program's function.

2

1.1 PROGRAM DESCRIPTION

The STAT program was originally written i n FORTRAN 77 and compiled w i t h the IBM VSFORT 1.4.1 compiler. I t has since been modified t o be compatible w i t h the CRAY CFT 1.14BF4 compiler.

STAT provides for the numerical optimization of turboprop blades. The program's goal i s t o i te ra t ive ly improve the design of a blade by modification of the design variables of the analysis. The i n i t i a l blade, cal led the 'basel ine ' , i s described by the user ' s data se t . The output of the program i s a s e t of design variable values which describe improvements t o the baseline blade. User i n p u t t o the program may be categorized as follows:

1 . 2 . 3. 4.

Data which describes the baseline design Data which describes the design variables and constraints Data which controls the method of the optimization Data which controls the o u t p u t of information t o the user.

1.2 CATEGORIZATION OF MODULES

The STAT program consists of four logically different types of modules. The f i r s t o f these i s the analysis module. The analysis modules provide the system w i t h a description of the behavior of the blade tha t i s currently defined by the design vari ab1 es: The aerodynamic analysi s , the f i n i t e el ement analysi s , and the f l u t t e r analysis are examples of analysis modules.

The second type of module i s the objective function. The objective function i s the user ' s numerical description of goodness of a design, s ta ted so t ha t the best design produces the m i m i n u m value of the objective function.

Thirdly, STAT contains modules which comprise the optimizer. The optimizer uses the current design variable definit ion of the blade, the value of constraints on blade behavior and the value of the objective function t o suggest a modification t o the current blade (again s ta ted in terms of the design var iables) . STAT u t i l i ze s the ADS optimizer, developed by G. N . Vanderplaats (ref . 2 ) .

The final c lass of modules provides communication between the design vector description of the blade and the analysis modules. These routines a re collectively referred t o as the ADSREAD system. ADSREAD provides for the mnemonic description of the blade given by the user and a means for analysis routines t o re t r ieve a meaningful description of the current design. Understanding the operation of the ADSREAD subsystem i s necessary for understanding the STAT program's function.

3

2.0 THE ADSREAD SUBSYSTEM

The ADSREAD subsystem provides a means for the analysis modules t o access a description of the current blade design. This description i s by means of cubic spline curves which the user has defined through CURVE cards. Many of these CURVE cards are required; the curve name i s reserved and understood by the geometry and model pre-processors.

ADSREAD i s also used t o define variables and constraints on the model t o be optimized. This a b i l i t y i s provided through VARIABLE, CUTOFF and CONSTRNT cards. These cards are explained i n the STAT User's Manual (ref. 3).

There are three services provided by ADSREAD. First, ADSREAD allows the user t o describe the baseline model. Second, ADSREAD allows the user t o constrain and vary the model. Finally, ADSREAD provides a means t o interpret the ADS design variables i n terms of the design variables of the model.

All aspects of the model design, w h i c h equate t o design variables and define the dynamic description of the blade, are contained i n the array COEF. Primarily, this array contains cubic spline coefficients o f the current design variable curves. The COEF array i s acted upon i n the following ways.

Base1 i ne Description

Before entering the opt imizat ion loop , the program calls STATIN t o read the baseline description. The data read describes the design by means of abscissa and ordinate curve definitions w h i c h parameterize the design. The curve description i s then translated i n t o cubic spline coefficients i n the routine OPT003. Both of these routines are visible from the main routine.

Current Curve Update

After each iteration of the opt imizat ion loop , ADS returns a new design vector. The design vector must then be interpreted i n terms of the curve(s) i t modifies. The routine OPT009, visible from the main routine, i s responsible f o r the t ranslat ion. Note t h a t a t the beginning of execution, the design vector is zero. This i s because the current design i s represented by a perturbation of the baseline design. T h a t i s , the current design i s equal t o the baseline design curve p l u s the delta a d d i t i o n t o t h a t curve provided by the ADS design vector.

Design Curve Val ue Retrieval

The analysis modules need a description of the blade t o be analyzed. Some of the information about this model i s found i n the da ta dedicated t o t h a t analysis (such as ASETs and SPCs o f the FEA). Most of the da ta w h i c h describes the current geometry of the model i s retrieved from the COEF splines using the routine OPTOOl. OPTOOl simply takes as i n p u t the name of the curve on w h i c h values are required and the abscissa values along t h a t curve where the values are required. The o u t p u t i s ordinate values o f t h a t curve.

4

3.0 PROGRAM FLOW CHARTS

This sec t i on dep ic ts t h e f l o w o f t h e STAT program, and descr ibes t h e f u n c t i o n o f each h igh- leve l module.

3.1 MAIN PROGRAM

FLOW ROUT1 NES

USED

START

I n i t i a l i z a t i o n

Read user i n p u t

Def ine o b j e c t i v e func t i on va r iab les

I n i t i a l i z e design curves

I n i ti a1 i ze ADS

I n i t i a l AERO ana lys i s

-Begin Approximate Opt imizat ion Loop Th is l oop terminates when ADS has found an optimum design (and r e t u r n s INFO = 01, o r when t h e maximum number o f i t e r a t i o n s (MXITER) has been exceeded, o r when the maximum number o f design steps (IDM) has been exceeded.

Ca l l op t im ize r f o r nex t design vec tor

Update design curves

Produce shape d e s c r i p t i o n o f a i r f o i l

F i n i t e E l ement Analys is (FEA)

STAT I N

ASSOCS

OPT003 OPT009

ADS

EFFICH

ADS

OPT009

5DS

FEARUN

I f FEA y i e l d s a s ingu la r s t i f f n e s s m a t r i x du r ing a warm-start : Then re- run FEA i n c o l d - s t a r t mode.

I f FEA y i e l d s a s ingu la r s t i f f n e s s m a t r i x du r ing a c o l d s t a r t : Then STOP

5

F1 ut ter analysis

Deflected geometry update

Aero analysis

Acoustic analysis

1 -P aerodynamic analysis

1 -P forced response

Objecti ve function

Constraint cal cul a t i ons

O u t p u t resu l t s

FLUTER

GAEROH

EFF I CH

DBNF

ONEP

ONEPFR

OBJF

DEFCON

REPORT

Update design curves w i t h f inal design variables and plot OPT009 final design variables

O u t p u t f inal resu l t s of approximate optimization REPORT

Determine i f suf f ic ien t da ta has been i n p u t t o perform a ref i ned analysi s

REF I NT

If data i s insuff ic ient : Then STOP

Begi n Ref i ned Anal ysi s

Produce refined shape description of optimum a i r fo i l

Refined f i n i t e el ement analysi s

IF FEA yiel ds a singul a r matrix: Then STOP

Refined f l u t t e r analysis (This i s no t available i n the NASA p u b l i c version)

Deflected geometry update

Refined aero analysis

Refined acoustic analysis ( T h i s i s not available i n the NASA public version)

O u t p u t t ab le comparing resu l t s of approximate and refined analyses.

STOP

BDS

FEARUN

FLUTRR

GAEROH

EFFICH

NO I SE

REFREP

6

3.2 STATIN

STATIN reads a separate ly due func t ion , Aero

FLOW

START

-

1 program i n p u t except f i n i t e element data (FEA data i s read t o t h e program's storage s t ra tegy) . Opt imizat ion, Ob jec t ive Analys is and Mesh generation data are read here.

ROUT1 NES USED


Process op t im iza t i on i n p u t contained on t h e f o l l o w i n g cards: OPTIMIZE VARIABLE CONSTRNT CURVE ABSC I SSA DEBUG CONSTANT DEPEND PLOT

PRIORITY *END OPT $ (comments) Performs i n i t i a l v a T i d i t y check.

ADSRD

CUTOFF MATERIAL LAY -UP

Process e f f i c i e n c y ana lys is i n p u t contained on t h e f o l 1 owi ng cards : BLADE ENV I RON A I RFOI L AXIALV FILR/R *END - EFF Performs i n i ' t i a l v a l i d i t y check.

Process o b j e c t i v e func t i on i n p u t contained on the f o l 1 owi ng cards: OBJTYPE BASELINE SENSE BLDDATA BLDFREQ BLDMASS BLDDEFL *END OPJ Performs i n i t i a l v a T i d i t y check.

Process geometry generation i nput contained on the fol 1 owing cards : G E OMG E N C H 0 RDTAB SPANTAB ATTACHMT *END GEN Performs i n i t i a l v a T i d i t y check.

*

RDEFF

RDOBJ

RDGGEN

RETURN

7

I 3.3 ASSOCS

I i

ASSOCS associates locations of the i n p u t arrays BASE and SENSE w i t h par t icular variables used by the objective function. By u s i n g this method rather than a d i rec t read into those variables, i t i s easier for the programmer t o change objective functions. The programmer assigns different meanings t o the f i e lds o f the BASE and SENSE cards and writes a new ASSOCS routine. i

FLOW ROUTINES

USED

START

Associate user i n p u t data i n arrays BASE and SENSE w i t h specified variables used by the objective function.

RETURN

I 8

I

I I

I

i ~

I

I I

I I I

I ~

t I

--Begin Loop 1 For i = 1.. .number of curves do

Verify tha t an ABSCISSA card has been i n p u t which matches the abscissa of curve(i 1.

If no match ex is t s Then

p r i n t e r ror message

STOP

Endi f

Save baseline coeff ic ients of curve( i ) i n array COEF.

Plot cu rve ( i )

-End Loop 1

3.4 OPT003

ENDIT

OPT002

PLOTEM

OPT004

9

3.5 OPT009

OPT009 transforms the baseline curves i n array COEF in to current curves based on the ADS design vector, X.

ROUT1 NES FLOW USED

START

In i t ia l iza t ion ZERO

-Begin Loop 1 For i = 1.. .number of curves do

If no variables or constants reference curve( i ) Then goto End Loop 1.

Begin Loop 2 For j = 1.. .number of design variables do

If design variable( j ) does not reference curve(i Then goto End Loop 2.

Create del ta design variable curve. X vector consis ts o f abscissa values contained i n VARABS and DEPLOC arrays. Y vector consists of del ta design variables contained i n ADS design variable array.

End Loop 2

Begin Loop 3 For j = 1.. .number of constants do

If constant( j) does not reference curve(i 1 Then goto End Loop 3.

Create constant curve. X vector consi'sts o f abscissa values obtained from CONSTANT cards. Y vector consists of ordinate values from CONSTANT cards.

I 1 -End Loop 3

Merge the del ta design variable curve and the constant curve t o form a single del ta design variable ( D D V ) curve.

F i t a cubic spline through the DDV curve and determine the coefficients for an interpolating polynomial.

VMERGE

BMFIT

10

I I Evaluate the DDV curve a t the points where the base curve ( i ) i s defined.

Add the del ta curve values t o the base1 ine curve(i ) store as the current curve(i 1.

i ne

and

Re-spl ine the current curve( i ) and place the coeff ic ients i n array COEF.

I f requested, pl o t current curve( i 1. 1 End Loop 1

Update COEF array w i t h any cutoff design variable.

Update COEF array w i t h any material angle design variable.

RETURN

BEVALE

OPT007

PLOTEM

OPT008

SCLRVR

11

3.6 ADS

ADS i s a general purpose numerical op t imiza t ion program con ta in ing a wide v a r i e t y o f a lgor i thms. I t s purpose i s t o minimize an o b j e c t i v e func t ion subject t o va r ious user-defined c o n s t r a i n t s .

FLOW

START

-

I f f irst time i n r o u t i n e Then

Check f o r Val i d i n p u t combinat ions

I n i t i a l ize s c a l a r parameters

Define work a r r a y s t o r a g e

RETURN

Endi f

Get s c a l a r s from work a r r a y

Set i d v = idv + 1

I f i d v l e number o f design v a r i a b l e s Then

C a l c u l a t e f ini te difference g r a d i e n t o f des ign va r i ab1 e( i dv)

Evaluate o b j e c t i v e func t ion

Begin Loop 1 For j = 1. . .number o f c o n s t r a i n t s

Eva1 uate c o n s t r a i n t (j

End Loop 1

O u t p u t va lues of g r a d i e n t s , o b j e c t i v e , and c o n s t r a i n t s

E l se

Set idv = 0

Perform one-dimensional s ea rch

ROUT1 NES USED

1 2

Eval uate objective function

For j = 1.. .number of constraints

Eval uate constraint( j )

-Begin Loop 2

-End Loop 2

O u t p u t values of gradients, objective, and constraints

Check convergence c r i t e r i a t o determine i f optimization i s complete

I f optimization i s complete Then output final resu l t s

Endi f

RETURN

1 3

3.7 EFFICI

EFFICH performs an aerodynamic ana lys i s on t h e a i r f o i l . It outputs propfan performance c h a r a c t e r i s t i c s and b lade 1 oads.

FLOW - START


Ret r ieve t / b , chord, and cone angle design curves from work a r ray (HOB, BOD, and CONE)

I f f i r s t t ime i n r o u t i n e Then

Retr ieve desi gn curves rep resen t i ng ' co l d ' geometry blade (BETA, CLD, XOR, YOR, and ZOR)

Set ' c o l d ' b lade angle

E l se

Ret r ieve design curves represent ing 'ho ' geometry b lade (BETAH, CLDH, XORH, YORH, and ZORH)

Ca lcu la te ' h o t ' b lade angl e

Endi f

Ca lcu la te a c t i v i t y f a c t o r s

Cal c u l a t e aerodynamic b l ade 1 oads

PNPINT

Calcu late propfan performance parameters ( t h r u s t , s h a f t h.p., e f f i c iency , . . . Store propfan data i n common f o r l a t e r use

RETURN

ROUTINES USED

OPTOOl

OPTOOl

OPTOOl

AFF I DC

L I NTHT

MNPANP

AIRFLT

3.8 BDS

BDS, the Blade Design System, i n t e r p o l a t e s des ign curve d a t a and ou tpu t s a se t o f r a d i a l splines which d e f i n e the a i r f o i l ex t e rna l s u r f a c e , l ead ing edge r a d i u s centers, s t ack ing p o i n t s , and t r a i l i n g edge r a d i u s centers.

FLOW ROUTINES

USED

START


In te rpol a t e b lade des ign curves from s p a r s e d e f i n i t i o n ( des i gn vari ab1 es ) t o dense def i n i t i on. Blade des ign curves a r e HOB, CLD, BOD, BETA, CONE, XOR, YOR, and ZOR.

OPT001

Cal cul a t e current b l ade ang le ANGLE

Cal cul a t e ex te rna l a i r f o i 1 con ic s e c t i o n s , s t a c k i n g poi nts, BDS004 l ead ing edge r a d i u s and t r a i l i n g edge radius c e n t e r s .

RETURN

1 5

3.9 FEARUN

FEARUN control s execution of the f i n i t e el ement i n p u t reader, mesh generator, and f i n i t e el ement analysi s.

ROUTINES FLOW USED

START

I f entering routine for the f i rs t time Then

In i t i a l i ze counters and storage arrays.

Allocate storage i n work array for i n p u t items.

Read user i n p u t f i n i t e element b u l k data.

E l se Then re t r ieve previous deflection vectors and b u l k data from scratch f i l e .

Endi f

Create bl ade f i n i t e element model , i ncl udi ng materi a1 def i n i t i on.

If requested, p r i n t b u l k data l ist ing.

Perform f i n i t e element analysi s.

If FEA yields a singular s t i f fnes s matrix Then RETURN

Recover s t resses of 1 aminate material s and cal cul a t e Tsai -Wu fa i 1 ure c r i t e r i a

Store current deflection vector and bulk da ta on scratch f i l e .

RETURN

-

INTINT

PREMAP

I NP UTT

GETMAT I NPUTT

FEAGEO

GEOD I G

FEA

P STCMP

P UTMAT

16

3.10 FLUTER

FLUTER determines the classical f l u t t e r stabi 1 i ty of propel 1 e r s w i t h swept blades i n a h i g h subsonic flow environment. I t takes beam equivalent mode shapes tha t have been derived from the plate f i n i t e element analysis, and calculates the damping r a t i o and natural frequencies fo'r six Mach number cases for the f i rs t four natural modes. A s t a l l f l u t t e r parameter and the f l u t t e r Mach number are output from this routine.

ROUT1 NES FLOW USED

START

In i t ia l ization

Define non-dimensional radial sections for analysis

Define the four solution modes

Cal cul a te the s t a l l f l u t t e r parameter

Define the six Mach number cases

10 Set npass = npass + 1

-

Set a i r density = a i r density * 0.7

For i = l...number of Mach number cases

Calculate the blade rotation needed to align the 3/4 chord w i t h the 3/4 re la t ive velocity(i

Cal cul a t e radius and re1 a t ive vel oci ty vectors

Def i ne aerodynamic sweep

Calculate mode shapes a t the previously defined analysis sections

Calculate chord, sweep, and twist a t the analysis sections

Calculate gap chord r a t io

Cal cul a te radi a1 span 1 engths

-Begin Loop 1

1 7

Assembl e aerodynamic modal matrix u s i n g cal cul ated section properties. Solve matrix t o obtain modal frequencies and damping.

Save frequencies and damping for number of modes for Mach number( i )

FDDS

I f any mode of Mach number case( i ) has damping g t 1 .O Then goto 10 (divergence)

If npass ge 20 Then goto 20

I f any mode of any Mach number case has damping I t 0.0 Then goto 10 ( i n s t a b i l i t y )

20 Cal cul a te f l u t t e r Mach number, correcting for cascade e f fec t

RETURN

18

3.11 GAEROH

GAEROH cal cul a tes I hot I propel 1 e r geometry.

FLOW

START

Ini t i a1 i t a t i on

Calculate change i n stacking due t o blade deflections from f.e.a.

Calculate change i n radial t i l t , tangential t i l t , axial t i l t and twist due t o blade deflections from f.e.a.

Calculate change i n camber due t o blade deflections from f.e.a.

Generate and s tore spline coefficients for 'hot ' geometry curves. These curves are BETAH (twist , CLDH (camber), XORH, YORH, AND ZORH ( t i l t ) .

ROUTINES USED

QSPL I N

OPT001

OPT002

RETURN

19

3.12 DBNF

DBNF cal cul a tes bl ade noi se and passage frequency.

FLOW

START

-

In i t ia l iza t ion

Calculate blade passage frequency as a function of t i p speed and blade diameter.

Cal cul a te corrected t i p speed, tpcor

Cal cul a t e corrected t i p cl earance, tccor

Calculate corrected ac t iv i ty factor , afcor

Calculate corrected sweep , swcor

Calculate corrected number of blades, nbcor

Calculate total blade noise as a function o f a l t i t ude , temperature, tpcor, tccor, afcor, swcor, and nbcor.

RETURN

ROUTINES USED

UNBAR

UNBAR

UNBAR

UNBAR

UNBAR

I 20

3.13 ONEPFR

ONEPFR calculates maximum s t a t i c and vibratory TSAI-WU s t resses , and outputs the maximum s t r e s s fa i lure ra t io .

FLOW ROUT1 NES

USED

START

In i t ia l iza t ion ZERO

Retrieve current f.e. deflection vectors and bulk data from scratch f i l e .

GETMAT

Cal cul a t e aerodynamic 1 oads ALOAD

If specified, output aerodynamic loads PFORCE

Calculate modal loads, generalized s t i f fnes s , and ampl i f ica t ion factors.

Calculate a steady s t r e s s Tsai-Wu value for each layer of every a i r fo i l element.

Calculate an equivalent Tsai-Wu stress by summing the Tsai-Wu stresses for each mode mu1 t i p 1 ied by the i r respective ampl i f ica t ion factors. The r e su l t will be the vibratory Tsai-Wu s t r e s s t o be measured on a 'Tsai-Wu Goodman Diagram'.

GETMAT PSTCMP

GETMAT P STCMP

Determine maximum stat ic /vibratory Tsai-Wu s t r e s s r a t i o from ' Tsai -Wu Goodman D i agram ' . RETURN

21

3.14 OBJF

OBJF uses da ta generated by the analysis modules, such a s stress, noise, efficiency, etc. . . , t o calculate an objective function value. The value of the objective function i s used by ADS t o evaluate design goodness.

FLOW

START

- ROUTINES

USED

In i t ia l iza t ion Z E R O

If objective function type eq 1 Then

Calculate scaled blade efficiency value, ddocl

Cal cul a t e scal ed bl ade weight Val ue, ddoc2

Cal cul a te scal ed b l ade noi se Val ue, ddoc3

Cal cul a te bl ade acquisition c o s t , ddoc4

Cal cul a t e b l ade maintenance cos t , ddoc5

Calculate objective function (de l ta d i rec t operating cos t ) by adding ddocl, ddoc2, ddoc3, ddoc4, and ddoc5.

Endi f

If objective function type eq 2 Then

Cal cul a t e frequency correl a t i on , ddocl

Cal cul a t e b l ade mass d i s tr i bution, ddoc2

Calculate modal deflections a t t i p , ddoc3

Cal cul a t e s t a t i c blade u n t w i s t , ddoc4

Calculate objective func t ion (aero-di fferences between fu l l and scale models) by adding ddocl , ddoc2, ddoc3, and ddoc4.

Endi f

RETURN

LNEARl

LNEAR1

22

3.15 DEFCON

DEFCON maps program a n a l y s , ~ o u t p u t s i n t o the appropriate positions of the TERMS array. NOTE: The positioning of TERMS values i s application dependent and defines the values of ITERM on CONSTRNT cards.

ROUT1 NES FLOW USED

START

Initialization

Frequencies for f i r s t 10 modes (From FEA) are stored in TERMS(1. . lo) .

Tsai-Wu layer stresses are stored i n TERMS(11. .30).

Flutter Mach number i s stored in TERMS(31).

Stall fluttek parameter i s stored in TERMS(32).

Power i s stored i n TERMS (33 1.

Activity factor i s stored in TERMS(34).

Max. von Mises stress i s stored in TERMS(35).

Ti p uncamber i s stored i n TERMS( 36 1.

. Tip untwist i s stored in TERMS(37).

Tip leading edge axial displacement i s stored in TERMS(38).

Tip trailing edge axial displacement is stored in TERMS(39).

One-p force response maximum stress failure ratio i s stored in TERMS(40).

RETURN

-

23

I 3.16 REPORT ,

REPORT outputs program resul ts . I

FLOW

START

-

Determine elapsed CPU time.

If optimization i s not complete (INFO ne 0) Then

O u t p u t resu l t s from current function c a l l .

If current function ca l l i s not a design move Then RETURN

Store design move resu l t s fo r summary p r i n t .

O u t p u t summary print every nine design moves.

RETURN

Endi f

O u t p u t f i nal optimi zat i on resul ts.

RETURN

ROUTINES USED

JOBTIM

24

4.0 FILE UNITS

The STAT program uses auxiliary f i l e s for data storage i n various ways. Particular FORTRAN u n i t numbers are used for certain program functions. Table I l i s t s the f i l e u n i t numbers. Any units n o t l i s t e d are available for use as scratch f i l e s by the user. All f i l e units l i s t e d are sequential access.

Table I Fi le Units

FORTRAN U n i t Number

5 6 7 8

10 14 17 18 19 20 21 22 24 26 30 39 40 41 42 43 44 45 46 47 48

Description

STAT i n p u t STAT o u t p u t Internal scratch f i l e Internal scratch f i l e Internal scratch f i 1 e Internal scratch f i l e Internal scratch f i l e Internal scratch f i l e STAT diagnostic output Internal scratch f i l e Internal scratch f i l e Internal scratch f i l e Internal scratch f i l e Internal scratch f i l e Mesh generator diagnostic output Finite element bulk data STAT summary report Fini te element scratch f i l e Fini te element scratch f i l e Finite element scratch f i l e Fini te element scratch f i l e F i n i t e element scratch f i l e Fini te element scratch f i l e Fini te element modeshapes Fini te el ement s t resses

Format

Card image Line pr inter Formatted Formatted Unformatted Formatted Formatted Unformatted Line pr inter Formatted Unformatted Unformatted Fo rma t ted Formatted Formatted Formatted Line pr inter Unformatted Unformatted Unformatted Unformatted Unformatted Unformatted Unformatted Unformatted

25

5.0 STAT COMMON BLOCKS

COMMON /ABCONV/ ICONVG( 10)

COMMON /ABDATA/ CLAFAB ( 1 00 , lO) ,CLGSAB ( 1 00, lO ) ,PHIAB ( 1 00,lO 1, . ALPHAB(100,10) ,BETAAB( lOO, lO) , I T N O ( l O )

COMMON /ABITER/ PHI INT ,CLA l

COMMON /ADSTMP/ X1 DM

COMMON /AERDAT/ THETA(15,6,2), AA(15,6,2), DIAG(15,6,2) , . CONST( 15,6,2), CMACH( 15,6,2), SMACH(15,6,2), . CFDP (1 5,6,2), SKEW(15,6,2 1

COMMON /AFCPIT/ AFXX,CLIXX

COMMON / A I RALZ/ ALZAOl ( 308 ) ,ALZA03 (268 ,ALZA07 (1 5

COMMON / A I RCDF/ CDFAOl (50 ) ,CDFA03 ( 1 1 ) ,CDFA08 ( 1 7 )

COMMON /AIRDAT/ F A I R ( 1000)

COMMON /ALLDAT/ T I T L E 1 (1 8) , T I T L E Z ( 1 8 ) , T I T L E 3 ( 7 ) ,DATA(2260)

COMMON /APEFFC/ EFFX

COMMON /ARGOTE/ TEMP2, POP2

COMMON /ARGOUT/ ALTO, TSS, SHPDD, AFF, DIAMM, XNBB, SWEPTT

COMMON /BARSAV/ ICTBAR, IDBAR(101, ICPBAR(10) , ICDBAR(10) ,

. TlBAR(lO),T2BAR(lO),T3BAR(lO) , IPABAR( lO) , . IMDBAR(10)

. I ELBAR( i o ) , IPDBAR( i o ) , IGI BAR( 10 1, IG2BAR( 10 1,

COMMON /BARX/ EE ( 500 1, GG ( 5 0 0 ) , R I Y ( 25 1, R I Z (25 , RJ ( 25), YA1( 25 , . R K l ( 2 5 ) ,RK2(25) . Z A l ( 25 ) , YA2 ( 25 ) , ZA2 ( 25 ,AREA ( 25 1 BAR ( 25 NBAR

COMMON /BDSC02/ TERAD,GOCODE

26

COMMON /BDSC03/ T10(48),T16(150),T63(48),T64(~~~),T65(48~y . T00(48), PX(22), PAN(55) T66(48) , TCA(96) , T230(96) , XZ(181, . NACA62 , NACA63, NACA64 , NACA65 COMMON /BIGMAT/ PHI(4OO),RW(6OOO),ZW(6OOO)

COMMON /CALSP/ EPS (50

COMMON /CASDAT/ SIGMAX(15,2),THETAG(15,Z),THETAB(15,6,2), . TAUB(15,2) COMMON /CCOM/ CHORD(15,2),ALCRAD(15,2),ALCPHI(15,2),ALCAXL(l5,2)

COMMON /CDPER/ DFR,DPR

COMMON /CINCOM/ CINPUT(15,2),ALCIRD(15,2),ALCIPH(15,2), . ALCIAX(15,2) COMMON /CLCDDT/ . CLSAV(15,6,2),CDSAV(l5y6,2~,ALPHA~15,6,2~yPHIHSD~l5,6,2~ , . CD0(15,6,2) ,CIRC(15,6,2),SAVCIR(15,6,2),FTRAN(15,6,2,3) COMMON /CMOMNT/ CMC4

COMMON /CMPNUM/ NCOMP

COMMON /CM104C/ CM14C ( 1 5,6,2 )

COMMON /COMPR / KC( 10)

COMMON /CONDAD/ PI,RADDEG,DEGRAD

COMMON /CONSTI/ RPM,SOUND, DENSTY ,VIMOM( 2 ) , BL, R(2 ) , STN, . THETA0 (2 ) ,HUBQ (2 ) , DPSI ,REV ,CP I I ,TOL ,CNSECT,SCOO( 2 1, RADCAS(2 1, . VORCOR,DCPDT,STACK,CTII ,DCTDT,ZHUB ,VKTASS,TIPM(2) ,RDTRAN(2) COMMON /CONST1 / PI I ,RC,R4PI (2) ,ON04PI ( 2 ,RSCSQ

COMMON /CONTS2/ DIA(2),OMGR(2),ZMSQ,UAX,PIND(2),ZJII,MU(Z)

COMMON /CORD/ ICID( 300 ) ,AI (3,300 1, AJ (3,300 ,AK( 3,300

COMMON /COSNSW/ COSS(l5,6,2)

COMMON /CPTHET/ NCP,ICPOK,THET0(10,2) ,CPCALC(lO) ,CTCALC(lO)

COMMON /CRSAV/ DATCR( 1 260,2 )

27

COMMON /CRUVS / VAIOV ( 1 0,2 ,VT IOV ( 1 0,2 1, LPRNT, I C R I T , ICR, K o N V , . CTX( 2 ) ,CPX(2 1 ,DIAMX(2 1 ,ZJXX( 2 1 ,BETAX(2

COMMON /CYC1/ I S 1 ( 6 0 0 ) , I S 2 ( 6 0 0 )

COMMON /CYJOIN/ NSEG , NSIDE, I S I D E l ( 50 1, I S I D E 2 (50

COMMON /C1 O/ F(175)

COMMON /DATIP/ D A T ( 7 0 0 )

COMMON /DZLETE/ DLEX, ZLEX, DTEX, ZTEX

COMMON /EFFICA/ EATA, BET75 , HP

COMMON /ELCONT/ I E L I D

COMMON /ELEPX / CLOCD(10) ,DFDR(10) ,DTDR(10)

COMMON /EMGEST/ E L I D , I S I L S (3 ,THETA, EPS ,THEST (3 ) , . TDFALT,FI2 ,FI3,FMU,Zl ,Z2, . AVGTMP ,MID1 ,MID2 ,MID3,MID4, R l ( 3 1, R2 ( 3 ,R3 (3 1, I C 1 , Ic2, I C 3

COMMON /EMGPRM/ IKGG,IMGG,NOGO,ICMBAR

COMMON /FCOM/ . FTOT(15,6,2),ALFRAD(15,6,2),ALFPHI(15,6,2),ALFAXL(l5,6,2), / FLTOT(15,6,2) ,ALFLRD(15,6,2),ALFLPH(15,6,2) ,ALFLAX(15,6,2) , . FDTOT( 1 5,6,2 ) ,ALFDRD (1 5,6,2 1, ALFDPH (1 5,6,2 1, ALFDAX( 1 5,6,2

COMMON /FLIGHT/ ZMO(15,2), ZJO(15,2)

COMMON /FLOWDT/ DENS(15,2),SOUN(15,2),VONVO(l5,2),URONVO(l5,2), . VZER0(15,2),VZEROB(16,2) COMMON /FLOWFD/ AOMT(501, VTOVZA(10,50), CMAA(10,50)

COMMON /FORCOM/ FRAD(15,2),FPHI(15,2),FAXL(15,2)

COMMON /FORCON/ ZMFS, ZMROT, P H I 0 1 0 ( 1 0 ) , A A A ( 1 0 )

COMMON /GAMUV/ GAMMA(101, U X ( l O ) , V X ( 1 0 )

COMMON /GAUSIN/ GCINPU(10,2), GDTHET(10,2), GTOVER(10,2), . GAFOIL(10,2) , GDESCL(10,2), GRSCIN(10,2), . GVONVO( 10,2), GURONV (1 0,2), GTHETA( 10,2 )

28

COMMON /GCDIMD/ GCDIMZ(15,lZ) ,GCDIMT(15,12) ,GCDIMR(15,12)

COMMON /GCKGSK/ GCK ( 1 00 1, GSK ( 100 1, I RGCK ( 1 00 1, I CGCK ( 1 00 1, NGCK, . IRGSK( 100) , ICGSK( 100) ,NGSK COMMON /GEODAT/ RSB( 16,Z ) ,ZSB(16,2 ) ,YSB(16,2 1, . RSBB(16,2),ZSBB(16,2),YSBB(16,2) ,PHIBB(16,2), . RSC (1 5,2 1, RSCC (1 5,2 1, ZSCC (1 5,2 ,YSCC (1 5,2 ,PHICC (1 5,2 1, . XSBB(16,Z) ,XSCC(l5,2) COMMON /GEOINP/ VONVOX( 16,2 ) ,CX( 16,2 1, DTHETX( 16,Z ) ,TOVERX ( 16,Z

COMMON /GEOMOD/ DESCLP ( 1 5,2

COMMON /GEOOUT/ DTHETA(15,2),AFOIL(15,2),DESCL(15,2), . TOVERC(15,2),BODD(15,2) COMMON /GGCKSK/ GGCK ( 1 00 ) , GGSK ( 100 ) , I RCK ( 1 00 ) , ICCK ( 1 00 ) , NGCKl , . IRSK( loo), ICSK( 100) ,NGSKl COMMON /HARMNC/ NHARM, I HARM( 1 00 1, LOOP

COMMON/HMTOUT/ HBUF(4)

COMMON /HSQSPL/ IPTNUM,TENSON,NSUB, IPT(200) ,COEFFX(300), . COEFFY(300) ,CHDVAL(300) ,ITYP,IMODE,ITRAP COMMON /INDEX/ INDX

COMMON /INDEX1 / . IBEGIN,IXCMGG,IXEEZ ,IXZ ,IXP002,IXKGGS,IXKDIF,IXZA ,IXPAA , . IXASET,IXAS2 ,IXSPC ,IXUSPC,IXPGG ,IXASFU,IXRBE ,IXRBEF,IXDZMl, . IXFORC,IXP001,IXEE20,IXARST,IXBUFF,IXPGGS,IXID ,IXICP ,IXX1

COMMON /INDEX2/ . IXX2 ,IXX3 ,IXICD ,IXIEID,IXIPID,IXIG1 ,IXIG2 ,IXIG3 ,IXTHET, . IXTl ,IXT2 ,IXT3 ,IXPIDA,IXMID1,IXMID2,IXMID3,IXT ,IXBSTF, . IXTSST,IXANSM,IXZlI ,IXZ2I ,IXMID4,IXG11 ,IXG12

COMMON /INDEX3/ . IXG13 ,IXG22 ,IXG23 ,IXG33 ,IXRHO ,IXA ,IXTREF,IXGEI ,IXST , . IXSC ,IXSS ,IXMSCI,IXMID ,IXCORD,IXUXl ,IXUXE ,IXUX3 ,IXMGS , . ISTART,IDZSAV COMMON /INDEX4/ . IXIFG ,IXFCID,IXFX ,IXFY ,IXFZ ,IXIFGl,IXFGl ,IXFGll,IXFGlZ, . IXIFG2,IXFGZ ,IXFG21,IXFG22,IXFG23,IXFG24,IXIMG ,IXMCID,IXFMX , . IXFMY ,IXFMZ ,IXIMGl ,IXFMGl ,IXMG11 ,IXMG12,IXMG2 ,IXFMGZ,IXMGZl, . IXMG22,IXMG23,IXMG24,IXFEXT

29

COMMON /INDEX5/ . IKGG ,IMGG ,IMELM ,IKELM ,IKECS ,IKSF ,IB001 ,IKNM ,IGOl , . IB002 ,IG02 ,IGM ,IKMM ,IDZ ,IFORCE,ISPAC ,IsPAC1

COMMON /INPTP/ UBHP, UPRPM, UALT, UVKTAS, UT

COMMON /INTDTl/ ITOT,KTOT,JTOT,NTOT,BJTOT,JTOT1,IBB,LTOT,NPROP, . MSI ZE , LTOTl COMMON /INTDT2/ NCOMPR,NEVARD,IPRMAT,IPROPT,IPNT,ITYPES,NCFLOW, . IWAKOP,NACWAK,IJUNK,ISKIN,ICASDE,ICAS,IDEBUG,MATSOL,NCBWAK, . IPCH,ITYPCS COMMON /IOUNIT/ IOIN,IOOUT,IODIAG,IDEBUG,IOKAAT,IOKAA1,IOKDLM, . IOKELM,IOMGG,IOMODE,IOSTRS COMMON /IOUNT/ NREAD,NWRITE,NPUNCH

COMMON /IUNITD/ IUNIT(2,2)

COMMON /JUNK99/ BLANGL( 90)

COMMON /KCLSAV/ XKCL ( 1 0 )

COMMON /MACHNO/ ZMO

COMMON /MATIN / MATID,INFLAG,ELTEMP,SINTH,COSTH

COMMON /MATOUT/ G3X3(6) ,RHOY ,ALPHAS(3) ,TZERO,GE,G2X2(3)

COMMON /MATSAV/ ANGS,ATTS

COMMON /MAXSIZ/ MAXGRD,MAXEL ,MAXPSL ,MAXMAT,MAXCOR,MAXRFC

COMMON /MCONED/ XMC(2) ,YMC(2),ZMC(2) ,XMCT(2) ,YMCT(E),ZMCT(2)

COMMON /MCRITJ/ ZMCRTJ(16)

COMMON /MCRITS/ YMCRIT(10)

COMMON /MCRIT2/ ZMCR2D(16)

COMMON /MHCONE/ NSTAT(6,2),XKCONE(15,6,2)

COMMON /MZERO / ZMSQ

COMMON /NETF/ ICALC ,XEFFA,XCTA, SEFF ( 3 1, YCTA( 3 ) , SARNO( 1 0 1, SVOV (1 0 1, . JRET COMMON /NORCOM/ ALNRAD(15,2) ,ALNPHI(15,2) ,ALNAXL(15,2)

30

COMMON /NUMCAS/ NNCASE,JJCASE,IPOREV

COMMON /OPTOPT/ NCALC

COMMON /PHICOM/NPHI ,DELPHI (1 6,37 ) ,COSDPH (1 6,37 ) ,SINDPH( 16,37

COMMON /PHIZER/ ABOVE(15,2)/ BELOW(15,Z)

COMMON /PLTFRM/ IPLTFM

COMMON /PRESCV/ UOVERV(10) ,VOVERV(10) ,SWIRLA( lO) ,UWOV0(10) , . TEMPR(lO),ZMWOMo(lO),PRESRA(1O),ZETAD ( 1 0 ) , H I H 0 2

COMMON /RECALL/ MATRIX ( 20 , l l ) , ITAPE, LPERC , MAXCAS , KERREC ,MBEST, I END

COMMON /REYNXX/ REYNOS(10)

COMMON /RFRC/ RFA,RFNl,RFN2,RFN3,RFDRPM

COMMON /RFRC8/ R F A 8 ( 8 ) ,RFN18(8) ,RFN28(8) ,RFN38(8) ,RFDRP8(8) , . I D R F 8 ( 8 )

COMMON /ROLL/ TRUNCT( 2 1 ,TRUNCI (2 1, ROLLUP ( 2

COMMON /SAVECM/ CMA1 ( lO) ,ZMETHD( lO) ,CMA(10) , IJWRIT

COMMON /SAVEPL/ DCPDX ( 1 5,6,2 1, DCTDX( 15,6,2 1, P H I I U E ( 15,6,2 1, . DELX(l5,2),DD(l5),DT(15),TL(2),QL(2),QOL(2),QIL(2),DQ(l5),PL(2), . H P L ( 2 ) ,VNT(15,6,?) ,VCT(15,6,2 ),VST(15,6,2),VTT(15,6,2), . DTL(l5),DTD(l5),DDL(l5),DDD(15),DQI(15),DQO(15) COMMON /SAVH/ KICON,KIFOR,KNTYPE,KNOF,KIPR,TBHP,TPRPM,TALT, . TVKTAS,TT,TPXI,TSl,TS2,TS3,TS4,PSZJ,PSZMN COMMON /SAVP/ PSZJ, P S S l , PSZMN, PSD342, PSD343

COMMON /SAVPSI/ S I N P S I ( 7 3 ) ,COSPSI(73) , P S I I ( 7 3 )

COMMON /SER16/ QFREQ(801) ,QREAL(801) ,QIMAG(801)

COMMON /STACOM/ STABAR(15,2) ,ALSRAD(15,2),ALSPHI(15,2) ,ALSAXL(15,2)

COMMON /STCSTR/ STRSTC ( 1 7,500 )

COMMON /STRS/ S(288),E(18),TT(54),P(36),AVGTHK,INERTA

COMMON /TANVEL/ V20V2A(10,50) , ITEST

COMMON /THDESV/ DTHETS( 1 0 , C W L S ( 1 0

31

COMMON /THICKD/ THK(15,2) ,ALTIRD(15,2),ALTIPH(15,2) ,ALTIAX(15,2)

COMMON /TIPDAT/ S,CO,LAMLE,LAMTE

COMMON /TITEL/ TITLE(10)

COMMON /TQLOAD/ RINl(l0) , XMC41(10), DTDRl (1 0) , DFDRl(l0) COMMON /TSOTYP/ ITSO,TSO,TEK,TEKTYP

COMMON /TWENTY/ X20(20) ,CL020(20) ,CLD20(20) ,TOB20(20) ,ZMCH20(20) , . ZMCOS (20) ,ZMIN20 (20) ,ZMEF20 (20) COMMON /TWISTC/ DTWIST(16,2), TWIST(16,2)

COMMON /TYPE/ ITYPE(500)

COMMON /UICOM/ UIR(15,6,2) ,UIT(15,6,2) ,UIZ(15,6,2)

COMMON /UUCOM/ UR(l5,2),UT(l5,2),UZ(15,2)

COMMON /VCOM/ - . ALPHAN(15,6,2 1 ,VS(15,6,2 1 ,VC( l5 ,6 ,2 ) ,VN(15,6,2) , . VTOT( 1 5,6,2 ) ,ALVRAD( 1 5,6,2 ,ALVPHI ( 1 5,6,2 ,ALVAXL( 1 5,6,2

COMMON /VIDAT/ VIS( 1 5,6,2 1, V IC ( 1 5,6,2 ,V IN ( 1 5,6,2

COMMON /VKARM / VKOPT

COMMON /VONCOM/ INCONQ, IXCl41

COMMON /WAKDAT/ KTRUCT(2) ,JTRUCT(2) ,JTRUCI(2)

COMMON /ZJ 225 2/ ZJ 2 ( 1 0

32

5.1 COMMON BLOCKS SORTED BY ROUTINE

Common

(BLNK)

ABCONV

ABDATA

AB ITER

ADSTMP

AERDAT

AFCPIT

A I RALZ

A I RCDF

A I RCDM

A I RDAT

ALFEXT

AL LDAT

R o u t i n e Names

ABFIX A I R F L CL1 BS INPUTA ONEP YAWAN

A B F I X

ABITR

AB I TR

ADS402

BLDGEO PERFOR

LCP I T R

AIRCDM A I R 2 4 I SOARF REYNLS

AIRCDF A I R 2 4 I SOARF REYNLS

AIRCDM A I R 2 4 I SOARF REYNLS

A I RFL CASARF LIFT24 SWPARF

AEROMO

ABFIX A I R F L CL1 BS EFFICH L I NTHT PRECOV VMOM

AB I TR A I R F L T CNCY KAPXX OPTNS ZLABEL

ONEP

CL1 AS

MA1 N

CALCGC SOLVEL

L I NTHT

A I R F L CASARF LIFT24 SWPARF



A I R F L T DRAG24 MCLPFN TH I KAR

AB I TR A I R F L T CNCY HUBXX L I NTRF RDEFF VMOM2

ABRAT AZPOS CPH444 L INTHT PRECOV

* ZNTEGR

COSN SOLVEN

L I NTRF




A IRFLX I SOAFL MCRCLO TMCRIT

AB RAT AZPOS CONECR INPUTA ONEP S I NGL Y AWAN

ACHART CL1 AS E F F I C L I NTRF RDEFF

F I N A I R VECTOR

AIRFLX I SOAFL MCRCLO TMCRIT



A I ROFF I SOARF RATARF VONKAR

ACHART CL1 AS COSN KAPXX OPTNS STAT I N ZLABEL

AEROMO

EFFICH

S I NGL

LMCONE VVECTR

AIROFF

RATARF VONKAR

A I ROFF

RATARF VONKAR

A I ROFF

RATARF VONKAR

A I R23

RENUM ZEROAL

AEROMO

CPH444

PERFOR

ZNTEGR

AEROMX

HUBXX

VMOM2

PCHOUT

A I R 2 3

RENUM ZEROAL

A I R 2 3

RENUM ZEROAL

A I R 2 3

RENUM ZEROAL

A I R24

REYNLS

AEROMX

E F F I C

PNPINT

33

APEFFC

ARGOT2

ARGOUT

BARSAV

BARX

BDSCOl

BDSC02

BDSC03

B I GMAT

CALSP

CASDAT

CCOM

CDPER

CINCOM

CLCDDT

CMOMNT

CMP N UM

CM104C

COMPR

CONDAD

CONSTI

34

EFFIC

EFF I CH

EFFICH

GTCOOR

BAR1

BDSCOl

BDSOl8

BGSCOl

MNPANP

ONEP

F I N A I R PCHOUT RWZW7

F I N A I R PCHOUT SOLVEN

L I NTHT


F I N A I R SOLVEN

A I RFLT

ONEP

F I N A I R

ONEP

ETR3D STR32D

BLDGEO GCWAKE L I NTRF PNPINT RWZW7 WRITGC

SINGL

L I NTHT

L I NTHT

EMGG

BDSOl8

BDSOl4

S ETMAT

FVECTR PERFOR SOLVEL

FVECTR PERFOR VECTOR

L I NTRF


FVECTR

F I N A I R

PERFOR

FEA

CALCGC INDVEL MNPANP PRWZW SOLVEL

L I NTRF

L INTRF

GEODIG

SOLVEL

I N T I A L PNP I NT SOLVEN

I N T I A L PNP I NT VVECTR

PCHOUT

I N T I A L PNPINT VVECTR

I NDVEL

I N T I NT

CHKINP I N T I A L NSTACO RWZW I N SOLVEN

PNPINT

INPUTT

SOLVEN

L I NTHT RWZWl VECTOR

L I NTHT SOLVEL WRITGC

PERFOR


PCHOUT

PSTRSS

EFFICH L I NTHT PCHOUT RWZWl SOLVIT

PRINX

L I NTRF

VVECTR

L INTRF

PNPINT

L I NTRF

PERFOR

REORDR

F I N A I R

PERFOR

VECTOR

NSTACO

NSTACO

NSTACO

SOLVEL

STR31 D

FVECTR

PHICAL

VVECTR

CONSTl

CONTSZ

CORD

COSNSW

CPTHET

CRSAV

CRUVS

CYCl

CYJOIN

c10

D A T I P

DZLETE

EFFICA

ELCONT

ELEPX

EMGDSl

EMGEST

EMGPRM

FCOM

BLDGEO INDVEL MNPANP PRWZW SOLVEL


CORDZR GMP C PGGl

F I N A I R

CTITER RWZW7

CPH444

CPH444

CYCLIC

CYCLCZ

c10

ONEPR

CALSWZ

EFFICH

BARl

ONEP

BARl I N T I N T

BARl STR31 D

EMGG

FVECTR

CALCGC I N T I A L NSTACO RWZWIN SOLVEN

CALCGC I N T I A L NSTACO RWZW I N SOLVEN

CTMASS GP6X6 PREFRC

PERFOR

F I N A I R SOLVEL

E F F I C

EFF I C

I NPUTT

CYCLIC

YAWAN

CONECR

PERFOR

EMGG

CYCLCZ PRINX

EMGG STR32D

ETR3D

PCHOUT

CHKINP L I NTHT PCHOUT RWZWl SOLVIT

CHKINP L I NTHT PCHOUT RWZWl SOLV I T

FEAGEO GP6X6B PREPRO

LCP I T R SOLVEN

SINGL

ONEP

PREPRO

I NPUTT

EMGPOM

EMA

ETR3D

P R I NX

PERFOR

F I N A I R L I NTRF PERFOR RWZW7 VECTOR

F I N A I R L I NTRF PERFOR RWZW 7 VECTOR

FEARUN INPUTT RELDEF

MNPANP

S I NGL

REDUCE

PREPRO

ETR3D

EMGG

P R I NX

FVECTR

PHICAL

VVECTR

FVECTR

PHICAL

VVECTR

GEOD I G

RLOAD

PCHOUT

VMOM2

P R I NX

ETR3D

PSTRSS

GC WAK E

PNPINT

WRITGC

GCWAKE

PNP I N T

WRITGC

GETVEC

TRANSD

PERFOR

PSTRSS

FEA

RELDEF

35

FLIGHT :

FLOWDT :

FLOWFD :

FORCOM :

FORCON :

F91 OUT :

GAMUV

GAUSIN :

GCDIMD :

GCKGSK :

GEODAT :

GEOI NP :

GEOMOD :

GEOOUT :

GGCKSK :

HARMNC :

HMTOUT :

36

F I N A I R SOLVEN

F I N A I R PCHOUT RWZW7

AEROMO

PCHOUT

CONECR

EFFICH

ONEP

L I NTHT

CALCGC

CYCLC2

BLDGEO I N T I A L NSTACO RWZW7




CYCLC2

INPUTT

ETR3D

I N T I A L VECTOR

FVECTR PERFOR SOLVEL

A I RFL

PERFOR

ONEP

PERFOR

L I NTRF

GCWAKE

CYCLIC

CALCGC L I NTHT PCHOUT SOLVEL




CYCLC3

PCHOUT VVECTR

I N T I A L PNPINT SOLVEN

CL1 BS

VMOM2

PNPINT

PNPINT

WRITGC

I NPUTT

F I N A I R L I NTRF PERFOR SOLVEN




PERFOR

L I NTHT RWZWl VECTOR

ONEP

FVECTR MNPANP PNPINT VECTOR




RWZWl

L I NTRF

VVECTR

GCWAKE

PRWZW VVECTR

GCWAKE

PRWZW VVECTR

GCWAKE

PRWZW VVECTR

GCWAKE

PRWZW VVECTR

SOLVEL

NSTACO

INDVEL

RWZWl

INDVEL

RWZWl

INDVEL

RWZWl

INDVEL

RWZWl

HSQSPL

INDEX

INDEX1

INDEX2

INDEX3

INDEX4

INDEX5

INPTP

INPT23

I NTDTl

I NTDT2

I O U N I T

CALSW2 QSPLIN

BDSO14

FEA

FEA

FEA

FEA

FEA

I NPUTA

I NP UTA

BLDGEO GCWAKE L I NTRF PNPINT RWZW7 WRITGC


ADDCD BMADD CNVRGl E I GEN EMGG FFORCE GETMAT GTMODE KGGl MAPPER MODPRT OPT005 PARAM PRINX PSTCMP REBAND REPORT SPRING STRPRT VMERGE

EFFICH

FEAGEO

FEAGEO

FEAGEO

FEAGEO

FEARUN

L INTHT

L I NTHT

CALCGC I NDVEL MNPANP PRWZW SOLVEL


ADSRD CHKLOG CNVRT EIGS EMGPOM FREQTB GMMATD I DENT KNN MATCMP ONEPFR OPT007 PFORCE PRTBBB QIJ REDUCE RESTOR STAT1 N STR31 D

GAEROH

FEARUN

FEARUN

FEARUN

FEARUN

ONEPFR

L I NTRF

L I NTRF

CHKINP I N T I A L NSTACO RWZW I N SOLVEN

CHKINP L INTHT PCHOUT RWZWl SOLVIT

ALOAD C NN COMAP ELAREA ETR3D FREQY GMPC I NPUTT LAJ A MERGE OPT001 OPT008 PGGl PRTBFB RAJA RELDEF RLOAD STRAIN STR32D

LMCONE

INPUTT

I NPUTT

INPUTT

I NPUTT

RDEFF

ONEP

EFF I CH L I NTHT PCHOUT RWZWl SOLVIT


ASEMBL C NSTR N COPY88 EMA FEA GEOD I G GP6X6 I N T I N T LAM1 N8 MGGl OPT002 OPT009 PRECMP PRTFFF RDEFF REORDR SCLRVR STRESS THKEFF

PERFOR

ONEPFR

ONEPFR

ONEPFR

ONEPFR

RDEFF

F I N A I R

PERFOR

VECTOR

FVECTR

P H I CAL

VVECTR

BANDER

CTMASS

FEAGEO

GP6X6B

LSTRAN

OPT003

PRELAM

RDGGEN

SPCARD

TRANSD

PNPINT

PREMAP

PREMAP

PREMAP

PREMAP

FVECTR

PHICAL

VVECTR

GCWAKE

PNPINT

WRITGC

BAR1

DEFCON

FEARUN

GTCOOR

MAIN

OPT004

PREPRO

RDOBJ

SPCARR

TSAIWU

3 7

IOUNT

I T E R

I U N I T D

J UNK99

KCLSAV

MACHNO

MAT I N

MATOUT

MATSAV

MAXSIZ

MCONED

MCRITJ

MCRITS

MCRIT2

MHCONE

MZERO

AF65A FV ECTR L I NTHT PERFOR RWZWl VECTOR

ONEP

BLDGEO INDVEL L I NTRF PRWZW SOLVEL

A B F I X A I R F L CL1 BS INPUTA PRECOV ZNTEGR

I SOARF

EFFICH

ETR3D

ETR3D

SCLRVR

INPUTT


A I RFLT

A I R 2 3

A I RFLT

F I N A I R SOLVEN

A I RFLT

BLDGEO GCWAKE L I NTRF PNPINT RWZW7 VVECTR


AB I T R A I RFLT CNCY KAPXX RDEFF

PNPINT

MAT

MAT


EFF I CH

I N T I A L VECTOR

CALCGC I NDVEL LMCONE PRWZW SOLVEL WAKMOD

CHKINP I U N I T D PCHOUT RWZWl SOLV I T

ABRAT AZP OS CPH444 ONEP S I NGL

STR31 D

STR31 D

F I N A I R L I NTRF P ERFOR SOLVEN

MCRCLO

PCHOUT VVECTR

CHKINP I N T I A L MNPANP RWZW I N SOLVEN WRITGC

F I N A I R L I NTHT PERFOR RWZW7 VECTOR

ACHART CL1 AS EFF I C OPTNS VMOM2


PERFOR

CSCDl

NSTACO

SWPCOR

FVECTR

PHICAL

VVECTR

AEROMO

EFFICH

YAWAN

GCWAKE

PRWZW VVECTR

RWZW

F I N A I R

PCHOUT

TIPGEO

GCWAKE

PNPINT

WRITGC

AEROMX

HUBXX

ZLABEL

INDVEL

RWZWl

SOLVEL

38

NETF

NORCOM

NUMCAS

OPTOPT

PHICOM

P H I ZER

PLTFRM

PRESCV

RECALL

REYNXX

RFRC

RFRC8

ROLL

SAVECM

SAVEPL

SAVH

SAVP

CPH444


ONEP

ONEP

CALCGC

PERFOR

EL AREA TOTARE

ONEP

ABFIX A I RFL CL1 BS I NPUTA PRECOV ZNTEGR

ABF I X A I R F L CL1 BS I NPUTA PRECOV ZNTEGR

CHKLOG RLOAD

CHKLOG

I N T I A L

AEROMO

PCHOUT

ONEP

L I NTHT

ONEP


WAKMOD

PNPINT

MA1 N

PRECOV

AB I TR A I R F L T CNCY KAPXX RDEFF


CTMASS

INPUTT

L I NTHT

AEROMX

PERFOR

L I NTRF

-~

SINGL


PRECMP

AB RAT AZPOS CPH444 ONEP SINGL

ABRAT AZPOS CPH444 ONEP SINGL

FREQTB

L I N T R F

ONEP


PRELAM

ACHART CL1 AS E F F I C OPTNS VMOMZ

ACHART CL1 AS E F F I C OPTNS VMOM2

FREQY

PNPINT

L I NTRF

PSTCMP

AEROMO

EFFICH

Y AWAN

AEROMO

EFFICH

YAWAN

I NPUTT

NSTACO

THKEFF

AEROMX

HUBXX

ZLABEL

AEROMX

HUBXX

ZLABEL

ONEPFR

39

SAVPSI

S E R l 6

STACOM

STCSTR

STRS

TANVEL

THDESV

THICKD

TIPDAT

T I T E L

TQLOAD

TSOTY P

TWENTY

TW I STC

TYPE

UICOM

UUCOM

40


S E R l 6


BAR1 STRPRT

EMGG

ABF I X A I RFL CL1 BS I NP UTA ONEP YAWAN

EFFICH


LMCONE

I NPUTT

EFFICH

EFFICH

TWENTY

F I N A I R

BANDER I NP UTT

FVECTR

BLDGEO SOLVEL



FEA

PRINX

ABITR A I R F L T CNCY KAPXX OPTNS ZLABEL

ONEP


TIPGEO

PERFOR

I NPUTA

MNPANP

CTRIA PREPRO

INDVEL

FVECTR SOLVEN

CHKINP L I NTHT PCHOUT RWZWl SOLV I T


ONEPFR

STR31 D

ABRAT AZP OS CPH444 L I NTHT PRECOV ZNTEGR

I N T I A L PNP I NT VVECTR

ONEP

PERFOR

EMA PRINX

PCHOUT

I N T I A L VECTOR

~



PRINX

STR32D

ACHART CL1 AS E F F I C L I NTRF RDEFF


OPTNS

PNPINT

EMGG STRPRT

PERFOR

NSTACO VVECTR

~

FVECTR

PHICAL

VVECTR

L I NTRF

P STCMP

AEROMO

EFFICH

SINGL

L I NTRF

SOLVEL

FEARUN

SOLVEN

PCHOUT

GC WAK E

PNPINT

WRITGC

NSTACO

PSTRSS

AEROMX

HUBXX

VMOM2

NSTACO

SOLVEN

GEOD I G

VVECTR

PERFOR

VCOM

V I DAT

VKARM

VONCOM

WAKDAT

ZJ 225 2

BLDGEO SOLVEL

FVECTR

A I R F L T

A I RFLT

CALCGC

ABFIX A I R F L CL1 BS I NPUTA PRECOV ZNTEGR

FVECTR SOLVEN

INDVEL

L I NTHT

I N T I A L


I N T I A L VECTOR

PCHOUT

L I NTRF

RWZW7

ABRAT AZPOS c P ~ 4 4 4 ONEP SINGL

N STAC 0 VVECTR

PERFOR

ACHART CL1 AS EFF I C OPTNS VMOM2

~ ~~

PCHOUT

SOLVEN

AEROMO

EFFICH

Y AWAN

PERFOR

VVECTR

AEROMX

HUBXX

ZLABEL

41

6.0 ADDING REFINED ANALYSIS MODULES TO STAT

Due t o the propr e t a r y nature of the STAT r e f i n e d acoustic and f l u t t e r modules, only dummy func t iona l modules are c u r r e n t l y provided i n the pub l i c d i s t r i b u t i o n version o f STAT. To enab le an independent user t o insert his/her own ana lyses i n t o STAT, sub rou t ine ca l l statements have been inc luded i n the r e f i n e d a n a l y s i s con t ro l s e c t i o n of the code. The fu l l a n a l y s i s c a l l i n g statements from the r e f i ned a n a l y s i s control modul e are i ncl uded bel ow, w i t h module i n p u t s and ou tpu t s l i s t e d .

SUBROUTINE FLUTRR( NSTAS,GL ,GT,GM,NFREQ,DGM,FREQX,GENMAS,XNB, 1 RPM,SOS,RHO,STALL,FMNEW,IDBG08,INFO,LOOPK)

C C REFINED FLUTTER ANALYSIS C C INPUT C C C C C C C C C C C C C C C C C C C C C C C C C C C C

NSTAS GL GT GM

NFREQ DGM

FREQX GENMAS XNB RPM sos RHO I DBG08

INFO

LOOPK

Number o f r a d i a l stations Leading edge d i sp laced geometry - xyz coord ina te s ( i n . T r a i l i n g edge d i sp laced geometry - xyz coord ina te s ( i n . M i d-chord d i sp l aced geometry - xyz coord ina te s ( i n . Note: G L , GT, and GM are the f in i t e element

coord ina te s f o r the h o t ( running posit ion b lade , and a r e ou tpu t from the f i n i t e element a n a l y s i s . The nodal p o s i t i o n s a l i g n w i t h the locat ions a t wh ich the mode shapes, DGM, are output .

Number of f r equenc ie s (hz ) Mode shapes a t mid-chord i n the swept normal coord ina te system f o r a l l six degrees of freedom ( i n . and r ad . ) Natural f r equenc ie s ( h z ) General i zed masses ( i n-1 b-s**2 Number of b l ades Propel 1 er speed ( rpm Speed o f sound ( f p s ) Air dens i ty ( s l u g s / cu. f t . ) Debug i n d i c a t o r

Optimization status i n d i c a t o r

des i gn i terat ion

0 - Skip d i a g n o s t i c messages 1 - Print d i a g n o s t i c messages

0 - Optimizer found an optimum des ign 1 - Refined a n a l y s i s being performed a t reques ted

Approximate opt imizat ion loop counter

C OUTPUT C STALL - S t a l l f lu t te r parameter C FMNEW - Classical f lu t te r Mach number, least s t a b l e mode C C

42

REAL*8 GL, GT, GM, FREQX, GENMAS, DGM DIMENSION GL(20,3), GT(20,3), GM(20,3), FREQX(51, GENMAS

1 DGM( 20,6 , 5 )

C C User coding C

RETURN END

SUBROUTINE NO1 SE (XMO, XMT , TEMP ,XNB , DIAM, X , HOB, BOD , CGA, ACB , FAD, BET, 1 CLX ,CDX, REL ,TIPCL ,POP ,CLD ,CRT, SWP ,EXP , BPFl ,TDB1 ,WORK )

C C REFINED ACOUSTIC ANALYSIS C C INPUT C C C C C C C C C C C C C C C C C C C C C C C C C C

XMO XMT TEMP XNB D I A M X HOB BOD C GA ACB FAD BET CLX CDX REL TIPCL POP CLD C RT

SWP EXP

WORK

C OUTPUT C BPFl c SPL1 C C

F l i g h t Mach number T i p r o t a t i o n a l Mach number Ambient temperature (F) Number o f blades B1 ade diameter ( f t ) Gauss s t a t i o n s and t i p s t a t i o n (X(1 )= roo t X ( l l ) = l . O ) Thickness t o chord r a t i o a t 10 Gauss s t a t i o n s Chord t o diameter r a t i o a t 10 Gauss and t i p s t a t i o n C.G. over diameter a t 10 Gauss s t a t i o n s Aero center ( f rom 1.e. t o c.g.1 a t 10 Gauss s t a t i o n s Face al ignment over diameter a t 10 Gauss s t a t i o n s Blade Twis t (Beta) a t 10 Gauss s t a t i o n s L i f t c o e f f i c i e n t a t 10 Gauss s t a t i o n s Drag c o e f f i c i e n t a t 10 Gauss s t a t i o n s Sect ion r e l a t i v e Mach number (10 Gauss s t a t i o n s ) T i p c l earance ( i n b l ade diameters ) Pressure r a t i o Design l i f t c o e f f i c i e n t a t 10 Gauss s t a t i o n s 2-D c r i t i c a l Mach numbers a t 10 Gauss s t a t i o n s

(Created i n Subroutine EFFICH o f t he aero module) Aerodynamic sweep a t 10 Gauss s t a t i o n s Sweep exponents a t 10 Gauss s t a t i o n s

(Created i n Subroutine EFFICH o f t h e aero module) Work array, used as scra tch storage - 280,000 Words o f storage are a v a i l ab1 e.

Frequency o f b l ade passage harmonic Maximum SPL loca ted on fuselage surface, db

43

6.1 WORK STORAGE ARRAY

The STAT program i s a large, multi-disciplinary system, ty ing together a number of diverse analyses. Due t o the number o f program modules employed, computer storage space has always been i n short supply. To provide adequate storage w i t h o u t requiring program overlays, STAT utilizes a large work storage area (currently 280,000 words i n length) t h a t i s accessible f o r use by a l l modul es.

W i t h i n the approximate opt imizat ion loop, this work array contains details of the f ini te element mesh, as well as displacement and stress results, and vibratory mode shapes. These arrays are used by the f i n i t e element module, the geometry update module, the f lut ter module, and others. Areas of the work array beyond the space required for the above matrices may be used as temporary scratch storage space by any of the modules, t h u s alleviating local matrix storage requirements.

Due t o the higher storage requirements of detailed, refined analyses, the biggest core storage requirements are seen i n the f i n a l , refined analysis step. For refined analyses, the entire work storage area i s available. This use of local scratch storage i s recommended where possible t o reduce overall storage requirements.

I 44 I

7.0 JCL FOR THE CRAY COS VERSION OF THE STAT PROGRAM

This sec t ion i s intended t o prov ide i n s t r u c t i o n s f o r s e t t i n g up j o b con t ro l f o r STAT on the NASA-Lewis Research Center CRAY XMP u t i l i z i n g COS 1.14BF4. Note t h a t t h i s s e t o f i n s t r u c t i o n s i s intended as a gu ide l i ne only; dataset names may vary and l o c a l system modi f i ca t ions may necess i ta te JCL mod i f i ca t ions .

7.1 EXECUTING THE STAT PROGRAM

The f o l l o w i n g JCL procedure may be submitted from VM o r TSS. It w i l l execute STAT and rou te the output, d iagnost ic , and summary r e p o r t f i l e s back t o the f ront -end machine.

Determining the exact t ime requ i red f o r a STAT op t im iza t i on run i s a complex task, and very problem dependent. Experience, however, has shown t h a t t he f o l l o w i n g formula provides a good t ime est imat ion:

Time = 8 * (NDV * 20 + 30) seconds, NDV = number o f design var iab les.

JOB, JN=jobname ,MFL=1000000,T=tlme. ACCOUNT,AC=acct,APW=pw. ACCESS,DN=STAT,PDN=STATLIB,ID=SMSTAT,OWN=SMSTAT. LDR,DN=STAT,LIB=IMSLLIB. DISPOSE,DN=FT19,SDN=DIAG. DISPOSE ,DN=FT40 ,SDN=REPORT. /EOF I n s e r t STAT i n p u t data here /EOF

7.2 UPDATING THE STAT PROGRAM

The f o l l o w i n g JCL procedure may be submitted from VM o r TSS. It w i l l comp FORTRAN r o u t i n e ( s 1. and update t h e STAT ob jec t the f ront -end machine.

NOTE: P r i o r t o submi t t ing t h i s procedure, t he access t o STATLIB from u s e r i d SMSTAT.

JOB, J N=jobname ,MFL=1 00000, T=time. ACCOUNT,AC=acct,APW=pw. ACCESS,DN=$OBL ,PDN=STATLIB, ID=SMSTAT,OWN=SMST CFT . BUILD. DELETE, DN=$OBL .

l e module. Output i s sent back t o

user must be permi t ted WRITE

SAVE,DN=$NBL ,PDN=STATLIB, ID=SMSTAT,OWN=SMSTAT,PAM=R. /EOF I n s e r t FORTRAN update( s) here /EOF

45

8.0 REFERENCES

1. Brown, K. W . , Structural Ta i lo r ing of Advanced Turboprops (STAT) In te r im Report, NASA CR 180861, August 1988.

2. Vanderplaats, G. N . , H. Sugimoto and C. M. Sprague, "ADS-1: A New General Purpose Optimization Program, " AIAA 24th S t r u c t u r e s , S t r u c t u r a l Dynamics and Materi a1 s Conference, Lake Tahoe, Nevada, May 1 983.

3. Brown, K. W. and P. R. Harvey, S t r u c t u r a l T a i l o r i n g o f Advanced Turboprops (STAT) User's blanual ( D r a f t ) , P r a t t & Whitney PWA-5967-43, March 1987.

46

DISTRIBUTION LIST

NASA-Lewis Research Center A t tn : Cont rac t ing O f f i c e r , MS 500-313 21 000 Brookpark Road Cleveland, OH 44135

NASA-Lewis Research Center A t tn : Tech. Report Contro l , MS 60-1 21 000 Brookpark Road Cleveland, OH 44135

NASA-Lewis Research Center A t tn : Tech. U t i l i z a t i o n O f f i ce , MS 7-3 21 000 Brookpark Road Cleveland, OH 44135

NASA-Lewi s Research Center A t tn : D iv Contract F i l e , MS 49-6 (2 cop ies) 21 000 Brookpark Road Cleveland, OH 44135

NASA-Lewis Research Center A t tn : L ib ra ry , MS 60-3 21 000 Brookpark Road Cleveland, OH 44135

NASA-Lewis Research Center A t tn : Adv. Turboprop Pro jec t , MS 86-7 21 000 Brookpark Road Cleveland, OH 44135

NASA-Lewis Research Center A t tn : R. E. K ie lb , MS 49-8 21 000 Brookpark Road Cleveland, OH 44135

NASA-Lewis Research Center At tn : D. A. Hopkins, MS 49-8 (2 cop ies) 21 000 Brookpark Road Cleveland, OH 44135

NASA-Lewis Research Center A t tn : C. C. Chamis, MS 49-8 21 000 Brookpark Road Cleveland, OH 44135

NASA-Lewis Research Center A t tn : L. Berke, MS 49-6 21 000 Brookpark Road Cleveland, OH 44135

NASA-Lewi s Research Center A t tn : L. J. K i r a l y , MS 23-3 21 000 Brookpark Road Cleveland, OH 44135

NASA-Lewis Research Center At tn : T. 0. Cressmaa, MS 86-10 21 000 Brookpark Road Cleveland, OH 44135

Nat ional Aeronautics & Space

At tn : NHS-22/Library Washington, DC 20546

Admin is t ra t ion

NASA S&T In fo rmat ion F a c i l i t y A t tn : Acquis. Dept. (5 copies) P. 0. Box 8757 B.W.I. A i r p o r t , MD 21240

NASA Ames Research Center A t t n : L i b r a r y Ma i l Stop 202-3 M o f f e t t F i e l d, CA 94035

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NASA Langley Research Center At tn : L i b r a r y Mail Stop 185 Hampton, VA 23665-5225

NASA Langley Research Center A t tn : M. F. Card Mai l Stop 244 Hampton, VA 23665-5225

NASA Goddard Space F l i g h t Center A t t n : 252/Li b r a r y Greenbelt, MD 20771

NASA LBJ Space Center At tn : JM6/Li b r a r y Houston, TX 77001

47

DISTRIBUTION LIST (cont inued)

NASA Marshall Space F l i g h t Center A t t n : AS61 /L ib ra ry Marshal 1 Space F1 i g h t Center, AL 3581 2

J e t Propul s i o n Laboratory A t t n : L i b r a r y 4800 Oak Grove Dr i ve Pasadena, CA 91103

AFFDL /FBE At tn : D. W. Smith Wright-Patterson AFB, OH 45433

A i r Force Aero. Propuls ion Lab. A t tn : N. Khot Wright-Patterson AFB, OH 45433

A i r Force Systems Command Aeronautical Systems D i v i s i o n At tn : L ib ra ry Wright-Patterson AFB, OH 45433

Department o f t h e Army U. S. Army Ma te r ia l Command At tn : AMCRD-RC Washington, DC 2031 5

U. S. Army M i s s i l e Command Redstone S c i e n t i f i c In fo . Center At tn : Document Sect ion Redstone Arsenal, AL 35808

Commanding O f f i c e r U. S. Army Research O f f i c e (Durham) A t t n : L i b r a r y Box CM, Duke S t a t i o n Durham, NC 27706

Bureau o f Naval Weapons Department o f t he Navy At tn : RRRE-6 Washington, DC 20360

Commander, U. S. Naval Ordnance Lab. At tn : L ib ra ry White Oak S i l v e r Springs, MD 2091 0

D i rec to r , Code 61 80 U. S. Naval Research Laboratory A t t n : L i b r a r y Washington, DC 20390

Aerospace Corporat ion At tn : Library-Documents 2400 E. E l Segundo Blvd. Los Angeles, CA 90045

Boeing Company A t t n : L i b r a r y Wichita, KA 67201

General Dynamics A t t n : L i b r a r y P. 0. Box 748 F o r t Worth, TX 76101

General Dynami cs/Convai r Aero. A t t n : L i b r a r y P. 0. Box 1128 San Diego, CA 92112

General E l e c t r i c Company At tn : D r . R. L. McKnight, MS K221 I n t e r s t a t e 75, Bldg. 500 C inc inna t i , OH 4521 5

Grumman A i r c r a f t Eng. Corp. A t t n : L i b r a r y Bethpage, Long Is land, NY 11714

Grumman A i r c r a f t Eng. Corp. A t tn : H. A. Armen Bethpage, Long Is land, NY 11714

Lawrence Livermore Laboratory A t t n : L i b r a r y

Livermore, CA 94550 P. 0. BOX 808, L-42

McDonnell Doug1 as A i r c r a f t Corp. A t t n : L i b r a r y P. 0. Box 516 Lambert F i e l d , MO 63166

48

Report Documentation Page 1. Report No.

NASA CR-182164 2. Government Accession No.

7. Authorkl

I

I K. W. Brown and P. R. Harvey

17. Key Words (Suggested by AuthorWJ

Approximate Analysis ; Mathematical Opt imiza t ion ; Objec t ive Function; Ref i ned Anal y s i s ; User I n s t r u c t i o n ; I Input ; O u t p u t

I

9. Performing Organization Name and Address

UNITED TECHNOLOGIES CORPORATION P r a t t & Whi tney , Commercial Engineering 400 Main S t . , East Har t ford , CT 061 08

18. Distribution Statement

1 12. Sponsoring Agency Name and Address

[ Uncl a s s i f i e d

National Aeronautics and Space Administration Lewis Research Center 21 000 Brookpark Road, C1 eve land , Ohio 441 35

15. Supplementary Notes

Program Manager: D. Hopkins 1 NASA-Lewi s Research Center, C1 eve1 and, Ohio

Unc las s i f i ed 49

3. Recipient's Catalog No.

5. Report Date

March 1989 6. Performing Organization Code

8. Performing Organization Report No.

PWA-5967-51 IO. Work Unit No.

It. Contract or Grant No.

NAS3-23941

13. Type of Report and Period Covered

Programmer I s Manual 14. Sponsoring Agency Code

16. Abstract

The S t r u c t u r a l T a i l o r i n g o f Advanced Turboprops (STAT) computer program was developed t o perform numerical op t imiza t ions on h ighly swept propfan b lades . T h i s manual d e s c r i b e s the f u n c t i o n a l i t y o f the STAT system from a p r o g r a m e r ' s viewpoint. I t provides a top-down d e s c r i p t i o n o f module intent and i n t e r a c t i o n . The purpose o f t h i s manual i s t o f a m i l i a r i z e t h e programmer w i t h t h e STAT system should he/she wish t o enhance o r v e r i f y the program's func t ion .

NASA FORM 1626 OCT

Northrop Space Laborator ies A t t n : L i b r a r y 3401 West Broadway Hawthorne, CA 90250

DISTRIBUTION LIST (cont inued)

North American Rockwell, Inc. Rocketdyne D i v i s i o n At tn : L ib ra ry , Dept. 596-306 6633 Canoga Avenue Canoga Park, CA 91304

North American Rockwell , Inc. Space & In fo . Systems Div. A t tn : L i b r a r y 1221 4 Lakewood B1 vd. Downey, CA 90241

Republ i c Avi a t i on Fai r c h i l d H i 11 e r Corporation A t t n : L i b r a r y Farmi ngdal e, NY 11 735

I I T Research I n s t i t u t e Technol ogy Center A t t n : L i b r a r y Chicago, I L 60616

Un i ted Technol og ies Corporation P r a t t & Whi tney At tn : L ib ra ry , MS 732-11 P. 0. Box 109600 West Palm Beach, FL 33410-9600

Uni ted Technol ogies Corporat i on P r a t t & Whi tney At tn : L ib ra ry , MS 169-31 400 Main S t r e e t East Har t fo rd , CT 06108

Uni ted Technol og ies Corporation Hamilton Standard At tn : A. Weisbrich Windsor Locks, CT 06096

Uni ted Technol ogies Corporation Hami 1 t o n Standard At tn : F. Metzger Windsor Locks, CT 06096

Uni ted Technol ogies Corporat i on Hami 1 t o n Standard At tn : R. Sherman Windsor Locks, CT 06096

Uni ted Technol og i es Corporat ion Hami 1 t o n Standard At tn : J. Baum Windsor Locks, CT 06096

Uni ted Technol og ies Corporat i on Hami 1 t o n Standard At tn : B. Gatzen Windsor Locks, CT 06096

49